CN208476509U - The test fixture and test device of aircraft head-shield - Google Patents
The test fixture and test device of aircraft head-shield Download PDFInfo
- Publication number
- CN208476509U CN208476509U CN201820823723.5U CN201820823723U CN208476509U CN 208476509 U CN208476509 U CN 208476509U CN 201820823723 U CN201820823723 U CN 201820823723U CN 208476509 U CN208476509 U CN 208476509U
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- frame
- test fixture
- rolling disk
- shield
- aircraft head
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Abstract
The utility model discloses the test fixture and test device of a kind of aircraft head-shield, which includes: chassis；Pitching frame is rotatably connected with the chassis, wherein the pitching frame is rotated around horizontal first axle；Orientation frame is rotatably connected with the pitching frame；Rolling disk is rotatably connected with the orientation frame, wherein the rolling disk is in the plane internal rotation where orientation frame.The test fixture of the aircraft head-shield of the application, can simplify device structure, reduce the expense of test.
Description
Technical field
The utility model relates to the test devices of a kind of test fixture of aircraft head-shield and aircraft head-shield.
Background technique
The test fixture of usual aircraft head-shield is solid column support type steel construction, and figure is big, the function such as required transmission device
Rate is high, and cost is high, causes testing expense expensive.
In view of the above problems in the related art, currently no effective solution has been proposed.
Utility model content
For problem present in the relevant technologies, the utility model proposes the test fixtures and aircraft of a kind of aircraft head-shield
The test device of head-shield, using the rolling structure of the anti-bearing-type of panel type structure and roll direction, before realizing said function
It puts, simplifies the structure of equipment, greatly reduce the expense of test.
The technical solution of the utility model is achieved in that
One aspect according to the present utility model provides a kind of test fixture of aircraft head-shield, comprising: chassis；Pitching
Frame is rotatably connected with chassis, and wherein pitching frame is rotated around horizontal first axle；Orientation frame, with the rotatable company of pitching frame
It connects；Rolling disk is rotatably connected with orientation frame, and wherein rolling disk is in the plane internal rotation where orientation frame.
Embodiment according to the present utility model, chassis include two brackets, and two brackets are respectively provided with connecting pin, pitching frame
It is connect between two brackets and with two connecting pins.
Embodiment according to the present utility model, pitching frame are the frameworks of octagon, and two connecting pins are connected to and bow
Face upward the midpoint of a pair of of opposite side of frame.
Embodiment according to the present utility model, orientation frame are located in pitching frame；Orientation frame is rotated around second axis, and first
Axis is vertical with second axis.
Embodiment according to the present utility model, orientation frame are the framework of octagon, the middle point on a side of orientation frame
Set the midpoint for being connected to a side of pitching frame.
Embodiment according to the present utility model, rolling disk are located in orientation frame, and rolling disk is the framework of circular ring shape, rolling disk
It is connected at least two sides of orientation frame.
Embodiment according to the present utility model, test fixture further include radar supports and the radar that connect with radar supports
Rotational structure, radar rotational structure are connected on rolling disk, and radar rotational structure drives radar supports around third axis and the
Four axistyle rotation, third axis is vertical with the plane where orientation frame, and four axistyle rotation is parallel with the plane where orientation frame.
Embodiment according to the present utility model, test fixture further include the connecting rod in rolling disk, radar rotation knot
Structure is connected on rolling disk by connecting rod, and radar rotational structure is connected to the midpoint of connecting rod.
Embodiment according to the present utility model, wherein aircraft head-shield is mounted on rolling disk.
Other side according to the present utility model additionally provides a kind of test device of aircraft head-shield, including above-mentioned
The test fixture of aircraft head-shield.
The utility model can adjust the rotation in three directions by adjusting rotatable pitching frame, orientation frame, rolling disk
Angle simulates pitching, yaw and the rolling maneuver of aircraft respectively, and the different postures simulated in aircraft flight are tested.It compares
The structure of equipment is simplified under the premise of realizing said function in the prior art, greatly reduces the expense of test.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model
Some embodiments for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other attached drawings.
Fig. 1 is the schematic diagram according to the test fixture of the aircraft head-shield of the utility model embodiment；
Fig. 2 is the schematic diagram of the radar rotational structure in Fig. 1；
Fig. 3 is the structural schematic diagram of the rolling disk and orientation frame in Fig. 1.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art's every other embodiment obtained, all belongs to
In the range of the utility model protection.
Refering to what is shown in Fig. 1, including: chassis 10 according to the test fixture 100 of the aircraft head-shield of the utility model embodiment；It bows
Frame 20 is faced upward, is rotatably connected with chassis 10, wherein pitching frame 20 is rotated around horizontal first axle；Orientation frame 30, with pitching
Frame 20 is rotatably connected；Rolling disk 40 is rotatably connected with orientation frame 30, and wherein rolling disk 40 is in the plane where orientation frame 30
Interior rotation.
The rotational angle in three directions can be adjusted by adjusting rotatable pitching frame 20, orientation frame 30, rolling disk 40,
Pitching, yaw and the rolling maneuver of aircraft are simulated respectively, and the different postures simulated in aircraft flight are tested.Compared to existing
Technology simplifies the structure of equipment under the premise of realizing said function, greatly reduces the expense of test.
In some embodiments, aircraft head-shield (not shown) to be tested is mounted on rolling disk 40.
Referring still to shown in Fig. 1, chassis 10 includes two brackets 12 extended along the vertical direction, and two brackets 12 have respectively
There is connecting pin 14, pitching frame 20 is rotatably connected with two connecting pins 14；And the connecting line of two connecting pins 14 and pitching frame
20 first axle rotates overlapping of axles, that is to say, that the connecting line of two connecting pins 14 and the rotation overlapping of axles of pitching frame 20.It is excellent
Choosing, pitching frame 20 is the framework of an octagon, and pitching frame 20 is located between two brackets 12 of chassis 10, two brackets
12 connecting pin 14 is connected on the midpoint of a pair of of opposite side of pitching frame 20, when the opposite chassis 10 of pitching frame 20 is around first axle
When line rotates, 20 place plane of pitching frame generates different pitch angles.
Further, orientation frame 30 is in pitching frame 20, and orientation frame 30 surrounds second axis vertical with first axle
Line is vertical.That is, the rotary shaft of orientation frame 30 is vertical with the rotary shaft of pitching frame 20.When orientation frame 30 rotates about axis rotation
When turning, frame 30 place plane in orientation generates different azimuths.Preferably, rolling disk orientation frame 30 is the framework of octagon,
One of rolling disk orientation frame 30 while midpoint be connected to one of rolling disk pitching frame 20 while midpoint.It can lead to
The suitable connector 22 of setting at the link position of orientation frame 30 and pitching frame 20 is crossed, so that a side of orientation frame 30
Midpoint is rotatably connected to the midpoint on a side of rolling disk pitching frame 20.
Referring to figs. 1 and 2, it is preferred that rolling disk 40 is located in rolling disk orientation frame 30, and rolling disk 40 is circular ring shape
Framework, rolling disk 40 is connected at least two sides of rolling disk orientation frame 30, such as is connected to four sides of orientation frame 30
On.When plane internal rotation of the rolling disk 40 at 30 place of orientation frame, different roll angles can be generated accordingly.
In conjunction with shown in Fig. 1 and Fig. 3, test fixture 100 further includes radar supports 50 and the thunder that connect with radar supports 50
Up to rotational structure 60, radar rotational structure 60 is connected on rolling disk 40, and radar rotational structure 60 drives radar supports 50 to rotate,
With guinea pig relative to the rotation of head-shield.Specifically, radar rotational structure 60 can drive radar supports 50 to surround and orientation frame
The vertical third axis rotation of the plane at 30 places.Wherein, radar rotational structure 60 can also drive radar supports 50 surround with
The four axistyle rotation of plane in parallel where orientation frame 30.
Wherein, test fixture 100 further includes the connecting rod 70 in the rolling disk 40, and radar rotational structure 60 passes through
Connecting rod 70 is connected on rolling disk 40, and radar rotational structure 60 is connected to the midpoint of connecting rod 70.In the present embodiment,
The quantity of connecting rod 62 is two.
In conjunction with shown in Fig. 1 to Fig. 3, test fixture 100, can by rotatable pitching frame 20, orientation frame 30, rolling disk 40
Simulate outer layer head-shield three rotary freedoms pitching, yaw and the rolling maneuver of aircraft (respectively simulate) and internal layer head-shield two
A rotational freedom (rotation of the guinea pig relative to head-shield).When testing aircraft head-shield, aircraft head-shield is mounted on rolling
Different postures on disk 40, by adjusting three rotary freedoms, in analog aircraft flight；It adjusts on radar supports 50 simultaneously
The rotational angle in 2 directions, the analog aircraft position of radar with respect to head-shield in different postures.It should be appreciated that example in Fig. 1
The situation on the basis of pitch rotation freedom degree is arranged in the rotational freedom for showing yaw of property, illustratively shows thunder
It is established on the basis of rolling 40 freedom degree of disk up to the rotational freedom on bracket 50；Illustratively showing roll freedom is
Rolling disk 40 is whole to be rotated around orientation frame 30, but the hierarchical relationship of three rotary freedoms can determine according to actual needs.
In some embodiments, each freedom degree should be able to not be interfered under conditions of meeting and rotating angle requirement, be influenced.
Other side according to the present utility model additionally provides a kind of test device of aircraft head-shield, the aircraft head-shield
Test device include above-mentioned aircraft head-shield test fixture.
The above is only the preferred embodiment of the utility model only, is not intended to limit the utility model, all at this
Within the spirit and principle of utility model, any modification, equivalent replacement, improvement and so on should be included in the utility model
Protection scope within.
Claims (10)
1. a kind of test fixture of aircraft head-shield characterized by comprising
Chassis；
Pitching frame is rotatably connected with the chassis, and the pitching frame is rotated around horizontal first axle；
Orientation frame is rotatably connected with the pitching frame；
Rolling disk is rotatably connected with the orientation frame, and the rolling disk is in the plane internal rotation where orientation frame.
2. the test fixture of aircraft head-shield according to claim 1, which is characterized in that the chassis includes two brackets,
Two brackets are respectively provided with connecting pin, and the pitching frame is connect between described two brackets and with two connecting pins.
3. the test fixture of aircraft head-shield according to claim 2, which is characterized in that the pitching frame is octagon
Framework, two connecting pins are connected to the midpoint of a pair of of opposite side of the pitching frame.
4. the test fixture of aircraft head-shield according to claim 3, which is characterized in that the orientation frame is located at the pitching
In frame；The orientation frame is rotated around second axis, and the first axle is vertical with the second axis.
5. the test fixture of aircraft head-shield according to claim 4, which is characterized in that the orientation frame is octagon
Framework, one of the orientation frame while midpoint be connected to one of the pitching frame while midpoint.
6. the test fixture of aircraft head-shield according to claim 5, which is characterized in that the rolling disk is located at the orientation
In frame, the rolling disk is the framework of circular ring shape, and the rolling disk is connected at least two sides of the orientation frame.
7. the test fixture of aircraft head-shield according to claim 1, which is characterized in that further include radar supports and with institute
The radar rotational structure of radar supports connection is stated, the radar rotational structure is connected on the rolling disk, the radar rotation
Structure drives the radar supports to rotate around third axis and four axistyle, where the third axis and the orientation frame
Plane is vertical, and the four axistyle rotation is parallel with the plane where the orientation frame.
8. the test fixture of aircraft head-shield according to claim 7, which is characterized in that further include: it is located at the rolling disk
Interior connecting rod, the radar rotational structure are connected on the rolling disk by the connecting rod, the radar rotational structure
It is connected to the midpoint of the connecting rod.
9. the test fixture of aircraft head-shield according to claim 1, which is characterized in that the aircraft head-shield is mounted on described
On rolling disk.
10. a kind of test device of aircraft head-shield, which is characterized in that including aircraft nose described in any one of claim 1-9
The test fixture of cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820823723.5U CN208476509U (en) | 2018-05-30 | 2018-05-30 | The test fixture and test device of aircraft head-shield |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820823723.5U CN208476509U (en) | 2018-05-30 | 2018-05-30 | The test fixture and test device of aircraft head-shield |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208476509U true CN208476509U (en) | 2019-02-05 |
Family
ID=65219580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820823723.5U Active CN208476509U (en) | 2018-05-30 | 2018-05-30 | The test fixture and test device of aircraft head-shield |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208476509U (en) |
-
2018
- 2018-05-30 CN CN201820823723.5U patent/CN208476509U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220606 Address after: 2 / F, software building, No.9, Gaoxin Zhongyi Road, Nanshan District, Shenzhen City, Guangdong Province Patentee after: SHENZHEN KUANG-CHI METAMATERIAL TECHNOLOGY Ltd. Address before: 4 / F, software building, No.9, Gaoxin Middle Road, high tech Zone, Nanshan District, Shenzhen City, Guangdong Province Patentee before: KUANG-CHI CUTTING EDGE TECHNOLOGY Ltd. |
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| TR01 | Transfer of patent right |